Rotor blade force track sensing system and automatic span tracki

Details Rotor blade force track sensing system and automatic span tracki Rotor blade force track sensing system and automatic span tracki

1974-05-20

1976-02-17

Halvosa, George E. A.

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

73462, 244 1727, 416 31, 416500, B64C 1144

Patent

active

039387623

ABSTRACT:
In eliminating one-per-rev vibration in a helicopter due to rotor unbalance, a one-per-rev vibration signal manifestation of rotor unbalance is generated and sampled when the rotor blades are successively in alignment with a reference direction during each cycle of rotation of said rotor. A difference signal is generated from the samples to represent by magnitude and phase the character of the unbalance. The rotor is modified in magnitude proportional to the magnitude of the signal and in direction dependent upon the span and chord components of the signal. In one aspect the force track error signal is applied to the input of a cyclic pitch control actuator system dynamically to automatically correct span unbalance forces.

REFERENCES:
patent: 2936836 (1960-05-01), Ellis
patent: 3175786 (1965-03-01), Frank et al.
patent: 3228252 (1966-01-01), Trimble
patent: 3298443 (1967-01-01), Burkam et al.
patent: 3386031 (1968-05-01), Able et al.
patent: 3795375 (1974-03-01), Lemnious

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